Regenerating an additively manufactured component

Patent metadata

Field	Value
Publication number	US-9375782-B2
Application number	US-201414784857-A
Country	US
Kind code	B2
Filing date	Apr 17, 2014
Priority date	Apr 19, 2013
Publication date	Jun 28, 2016
Grant date	Jun 28, 2016

Abstract

One embodiment includes a method to regenerate a component ( 10 ). The method includes additively manufacturing a component ( 10 ) to have voids greater than 0 percent but less than approximately 15 percent in a near finished shape. The component ( 10 ) is encased in a shell mold ( 22 ). The shell mold ( 22 ) is cured. The encased component ( 10 ) is placed in a furnace and the component ( 10 ) is melted. The component ( 10 ) is solidified in the shell mold ( 22 ). The shell mold ( 22 ) is removed from the solidified component ( 10 ).

First claim

The invention claimed is:

1. A method to regenerate a component, the method comprising:
additively manufacturing a component to have voids greater than 0 percent but less than approximately 15 percent by volume in a near finished shape;
encasing the component in a shell mold;
curing the shell mold;
placing the encased component in a furnace and melting the component;
solidifying the component in the shell mold; and
removing the shell mold from the solidified component.

2. The method of claim 1 , wherein the component is additively manufactured to have voids greater than 0 percent but less than approximately 1 percent by volume.

3. The method of claim 1 , wherein the component is additively manufactured to have up to 15 percent additional material by volume in the near finished shape compared to a desired finished configuration.

4. The method of claim 3 , wherein the component is a blade or vane and the up to 15 percent additional material by volume is located at a root or a tip of an airfoil of the component.

5. The method of claim 1 , wherein encasing the component in a shell mold comprises encasing an entirety of the component in the shell mold such that an entire external surface of the component is covered by the shell mold.

6. The method of claim 5 , wherein encasing the component in the shell mold comprises a process of:
(a) dipping the entirety of the component in a slurry to form a layer of the shell mold on the entirety of the component;
(b) drying the layer of the shell mold; and
(c) repeating steps (a) and (b) until an acceptable shell mold thickness is formed to encase the entirety of the component.

7. The method of claim 1 , wherein the component is additively manufactured using at least one of selective laser sintering, selective laser melting, direct metal deposition, direct metal laser sintering, direct metal laser melting, and electron beam melting.

8. The method of claim 7 , wherein the component is additively manufactured to be of a metal selected from the group consisting of a nickel-based superalloy, cobalt-based superalloy, iron-based superalloy, and mixtures thereof.

9. A method to regenerate a component with internal passageways, the method comprising:
additively manufacturing the component to have voids greater than 0 percent but less than approximately 15 percent by volume with an internal passageway in a near finished shape;
filling the internal passageway with a slurry;
curing the slurry to form a core;
encasing the component in a shell mold;
curing the shell mold;
placing the encased component in a furnace and melting the component;
solidifying the component in the shell mold; and
removing the shell mold and core from the solidified component.

10. The method of claim 9 , wherein the core substantially conforms to a shape of the internal passageway of the component, and wherein the shell mold substantially conforms to a shape of the component.

11. The method of claim 9 , wherein the component is additively manufactured to have voids greater than 0 percent but less than approximately 1 percent by volume.

12. The method of claim 9 , wherein the component is additively manufactured to have up to 15 percent additional material by volume in the near finished shape compared to a desired finished configuration.

13. The method of claim 12 , wherein the component is a blade or vane and the up to 15 percent additional material by volume is located at a root or a tip of an airfoil of the component.

14. The method of claim 9 , wherein the component is additively manufactured using at least one of selective laser sintering, selective laser melting, direct metal deposition, direct metal laser sintering, direct metal laser melting, and electron beam melting.

15. The method of claim 14 , wherein the component is additively manufactured to be of a metal selected from the group consisting of a nickel-based superalloy, cobalt-based superalloy, iron-based superalloy, and mixtures thereof.

16. The method of claim 9 , wherein the slurry is selected from the group consisting of silica, alumina, zircon, cobalt, mullite, and kaolin.

17. The method of claim 9 , wherein the shell mold is selected from the group consisting of silica, alumina, zircon, cobalt, mullite, kaolin, and mixtures thereof.

18. The method of claim 9 , wherein encasing the component in a shell mold comprises encasing an entirety of the component in the shell mold such that an entire external surface of the component is covered by the shell mold.

19. The method of claim 18 , wherein encasing the component in the shell mold comprises a process of:
(a) dipping the entirety of the component in a slurry to form a layer of the shell mold on the entirety of the component;
(b) drying the layer of the shell mold; and
(c) repeating steps (a) and (b) until an acceptable shell mold thickness is formed to encase the entirety of the component.

Assignees

• United Technologies Corp

Inventors

• Mcbrien John
• Castle Lea Kennard
• Spangler Brandon W
• Xu Jinquan

Classifications

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• B22C7/02 Primary

  Lost patterns · CPC title

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B22C9/061

  Materials which make up the mould · CPC title